Weight & Balance Calculator
AVIATION TOOLS · AIRCRAFT LOADING
Weight & balance
A clear view of your load, limits, and center of gravity.
Find an aircraft or start a custom profile
Cessna 172S has referenced normal-category data. Other names are starter profiles requiring aircraft-specific arms and limits. Custom profiles support additional models; this is not a verified database of every aircraft.
CG envelope
Plotted points are phase endpoints. Connecting lines are visual guides, not a fuel-burn trajectory check. Envelope limits are interpolated only between entered weight rows.
Aircraft empty condition
Use the current aircraft record, not a generic empty weight.People, baggage & other loads
| Station | Weight | Long. arm | Lateral arm | Max weight | Limit group | Moment |
|---|
Usable fuel by tank
Enter fuel as weight in the selected units. Unusable fuel and oil already included in basic empty weight must not be added again. Burn amounts are per tank.
| Tank | Loaded weight | Taxi burn | Flight burn | Long. arm | Lateral arm | Max fuel weight |
|---|
Fuel volume → weight helper
Enter volume and the correct fuel density.
The density must be in the selected weight unit per selected volume unit. Copy the result into the appropriate tank. No automatic fuel-type density assumption.
Profile limits & CG envelope editor
Enter values from the applicable POH/AFM and supplements. Blank limits are unknown, not unlimited. A “within entered limits” result only checks configured values.
Longitudinal envelope
Ascending weight, forward CG, aft CG. Straight interpolation between rows.
| Weight | Forward | Aft |
|---|
Lateral envelope
Ascending weight, minimum signed arm, maximum signed arm. Use the aircraft datum/sign convention.
| Weight | Minimum | Maximum |
|---|
Combined station weight limits
Stations with matching group names share this maximum (for example, two baggage areas with a combined limit).
| Group name | Combined maximum |
|---|
Variable fuel moment tables
For a tank with a variable arm, enter fuel weight and total fuel moment in the current units, starting with 0 weight / 0 moment. Intermediate moments are linearly interpolated. Tables override fixed tank arms. These are full moments, not moment indexes divided by 100 or 1,000.
% MAC and maneuvering-speed estimate
VA estimate = reference VA × √(takeoff weight / reference weight), only at or below the reference weight. Use the aircraft's published speeds and restrictions. MAC is optional and does not replace an AFM envelope or operating limits.
What this calculator checks
Moment = weight × arm; CG = total moment ÷ total weight. Fuel remaining moments are recomputed at ramp, takeoff, and landing, including entered variable moment tables. Phase weights and CG coordinates are checked against the entered limits. Station and combined-group weight limits are checked separately. The zero-fuel point is informational unless an applicable zero-fuel limit is entered.
This tool supports configurable longitudinal and optional lateral loading models. It does not implement every aircraft's proprietary loading index, fuel-transfer sequence, lateral/longitudinal coupled envelope, floor-pressure limit, or structural loading rule. Transport aircraft and helicopters may require additional approved methods. Aircraft catalogue entries are not proof of full model support.
Save files contain both aircraft profile and current load. Load reads this tool's version 1 JSON format locally; no data is uploaded. No automatic persistence: keep your saved file. Undo can restore the previous replacement or row deletion.